초록 ▼

A gas turbine engine includes a supply of cooling fluid, a rotatable shaft, blade disc structure coupled to the shaft and having at least one bore for receiving cooling fluid, and a particle separator. The particle separator includes particle deflecting structure upstream from the blade disc structu

A gas turbine engine includes a supply of cooling fluid, a rotatable shaft, blade disc structure coupled to the shaft and having at least one bore for receiving cooling fluid, and a particle separator. The particle separator includes particle deflecting structure upstream from the blade disc structure, and a particle collection chamber. The particle deflecting structure deflects solid particles from the cooling fluid prior to the cooling fluid entering the at least one bore in the blade disc structure. The particle collection chamber is upstream from the particle deflecting structure and receives the solid particles deflected from the cooling fluid by the particle deflecting structure. The solid particles deflected by the particle deflecting structure flow upstream from the particle deflecting structure to the particle collection chamber.

대표청구항 ▼

1. A gas turbine engine comprising: a supply of cooling fluid;a rotatable shaft;blade disc structure coupled to said shaft and having at least one bore for receiving a first portion of cooling fluid;a plurality of pre-swirl passages that deliver the first portion of cooling fluid from said supply of

1. A gas turbine engine comprising: a supply of cooling fluid;a rotatable shaft;blade disc structure coupled to said shaft and having at least one bore for receiving a first portion of cooling fluid;a plurality of pre-swirl passages that deliver the first portion of cooling fluid from said supply of cooling fluid toward said at least one bore for cooling blades in a turbine section of the engine;a particle separator that separates solid particles from the first portion of cooling fluid after the first portion of cooling fluid passes through said pre-swirl passages and prior to the first portion of cooling fluid entering said at least one bore in said blade disc structure, said particle separator comprising: particle deflecting structure upstream from said blade disc structure, said particle deflecting structure deflects the solid particles from the first portion of cooling fluid prior to the first portion of cooling fluid entering said at least one bore in said blade disc structure; anda particle collection chamber upstream from said particle deflecting structure, said particle collection chamber receiving the solid particles deflected by said particle deflecting structure, wherein the solid particles deflected by said particle deflecting structure flow upstream from said particle deflecting structure to said particle collection chamber; andstructure defining a plurality of bypass passages in fluid communication with said supply of cooling fluid for supplying a second portion of cooling fluid from said supply of cooling fluid into an enclosed turbine rim cavity upstream from said blade disc structure, wherein the second portion cooling fluid flowing through said bypass passages does not interact with the first portion of cooling fluid flowing through said pre-swirl passages or with said particle separator, said plurality of bypass passages including a first set of bypass passages and a second set of bypass passages, the first and second sets of bypass passages having inlets that are located respectively in separate chambers of the gas turbine engine and in different radial locations. 2. The gas turbine engine according to claim 1, wherein said particle deflecting structure comprises a radially inwardly extending portion that extends radially inwardly from said blade disc structure. 3. The gas turbine engine according to claim 2, wherein said radially inwardly extending portion comprises a curved radially inner end portion that extends in the axial direction toward said particle collection chamber. 4. The gas turbine engine according to claim 3, wherein said particle deflecting structure further comprises an axially extending portion located radially outwardly from said end portion, said axially extending portion extends generally axially with a slight radially outward slope from said radially extending portion toward said particle collection chamber. 5. The gas turbine engine according to claim 1, wherein said particle collection chamber is defined at least in part by a portion of a shaft cover structure that extends about said shaft, the shaft cover structure also being the structure defining said at least one bypass passage. 6. The gas turbine engine according to claim 5, further comprising sealing structure for limiting leakage between the shaft cover structure and said particle deflecting structure. 7. The gas turbine engine according to claim 5, further comprising a static metering structure that does not move relative to said shaft cover structure, said metering structure associated with outlets of said bypass passages and comprising at least one linear flow passageway formed therein per bypass passage for permitting the second portion of cooling fluid in said bypass passages to pass linearly into the turbine rim cavity. 8. The gas turbine engine according to claim 7, wherein each said linear flow passageway is formed in said metering structure at an angle such that the second portion of cooling fluid flowing out of each said linear flow passageway has a velocity component in the direction tangential to the circumferential direction. 9. The gas turbine engine according to claim 1, further comprising a pre-swirl structure disposed about said shaft, said pre-swirl structure located upstream from said particle deflecting structure at outlets of said pre-swirl passages for supplying the first portion of cooling fluid to said particle deflecting structure, wherein the first portion of cooling fluid exiting said pre-swirl structure has a velocity component in a direction tangential to a circumferential direction in the same direction as the rotation direction of said shaft. 10. The gas turbine engine of claim 9, wherein a swirl ratio defined as the velocity component in the direction tangential to the circumferential direction of the first portion of cooling fluid exiting said pre-swirl structure to a velocity component of said shaft in the direction tangential to the circumferential direction is greater than one. 11. The gas turbine engine according to claim 9, wherein said pre-swirl structure remains stationary and does not rotate with said shaft during operation of the gas turbine engine, and said particle deflecting structure rotates with said shaft during operation of the gas turbine engine. 12. The gas turbine engine according to claim 9, wherein said particle deflecting structure is located in an annular cavity that spans between said pre-swirl structure and said blade disc structure. 13. A gas turbine engine comprising: a supply of cooling fluid;a rotatable shaft;shaft cover structure disposed about said shaft;blade disc structure coupled to said shaft and having at least one bore for receiving a first portion of cooling fluid;a plurality of pre-swirl passages that deliver the first portion of cooling fluid from said supply of cooling fluid toward said at least one bore for cooling a first row of blades in a turbine section of the engine;a particle separator that separates solid particles from the first portion of cooling fluid prior to the first portion of cooling fluid entering said at least one bore in said blade disc structure, said particle separator comprising: particle deflecting structure upstream from said blade disc structure, said particle deflecting structure deflects the solid particles from the first portion of cooling fluid prior to the first portion of cooling fluid entering said at least one bore in said blade disc structure; anda particle collection chamber that receives the solid particles deflected from the first portion of cooling fluid by said particle deflecting structure; anda pre-swirl structure disposed about said shaft and located at outlets of said pre-swirl passages, said pre-swirl structure located upstream from said particle deflecting structure for supplying the first portion of cooling fluid from said supply of cooling fluid to said particle deflecting structure, wherein the first portion of cooling fluid exiting said pre-swirl structure has a velocity component in a direction tangential to a circumferential direction in the same direction as the rotation direction of said shaft;structure defining a plurality of bypass passages upstream from said pre-swirl structure, said bypass passages in fluid communication with said supply of cooling fluid for supplying a second portion of cooling fluid from said supply of cooling fluid into a turbine rim cavity upstream from said blade disc structure, said plurality of bypass passages including a first set of bypass passages and a second set of bypass passages, the first and second sets of bypass passages having inlets that are located respectively in separate chambers of the gas turbine engine and in different radial locations; anda static metering structure that does not move relative to said shaft cover structure, said metering structure associated with outlets of said bypass passages and comprising at least one linear flow passageway formed therein per bypass passage outlet for permitting the second portion of cooling fluid in said bypass passages to pass linearly into the turbine rim cavity. 14. The gas turbine engine according to claim 13, wherein said particle collection chamber is located upstream from said particle deflecting structure such that the solid particles deflected by said particle deflecting structure flow upstream from said particle deflecting structure to said particle collection chamber. 15. The gas turbine engine according to claim 13, wherein said particle collection chamber is defined at least in part by a portion of said shaft cover structure, wherein said shaft cover structure also defines said bypass passages and said pre-swirl passages. 16. The gas turbine engine according to claim 15, wherein each of said pre-swirl structure and said shaft cover structure remains stationary and does not rotate with said shaft during operation of the gas turbine engine, and said particle deflecting structure rotates with said shaft during operation of the gas turbine engine. 17. The gas turbine engine according to claim 13, wherein each said linear flow passageway is formed in said metering structure at an angle such that the second portion of cooling fluid flowing out of each said linear flow passageway has a velocity component in the direction tangential to the circumferential direction. 18. The gas turbine engine according to claim 13, wherein said particle deflecting structure comprises a radially inwardly extending portion that extends radially inwardly from said blade disc structure and an axially extending portion that extends generally axially with a slight radially outward slope from said radially extending portion toward said particle collection chamber, said radially inwardly extending portion comprising a curved radially inner end portion that extends in the axial direction toward said pre-swirl structure. 19. The gas turbine engine according to claim 13, further comprising sealing structure for limiting leakage between said shaft cover structure and said particle deflecting structure. 20. The gas turbine engine according to claim 13, wherein said particle deflecting structure is located in an annular cavity that spans between said pre-swirl structure and said blade disc structure.